基于解析及特征造型的涡轮冷却叶片参数化设计

推进技术 ›› 2007, Vol. 28 ›› Issue (6): 637-640.

基于解析及特征造型的涡轮冷却叶片参数化设计

虞跨海,李立州,岳珠峰

西北工业大学力学与土木建筑学院;陕西西安710072;西北工业大学航空学院陕西西安710072;西北工业大学力学与土木建筑学院;陕西西安710072

发布日期:2021-08-15
基金资助:
国家自然科学基金(50375124,10472094);国家“八六三”基金项目(2006AA04Z401)

Parametric design for cooling turbine blades based on analytic and feature modeling

School of Mechanics Engineering and Civil Architecture,Northwestern Polytechnical Univ.,Xi’an 710072,China;School of Aeronautics,Northwestern Polytechnical Univ.,Xi’an 710072,China;School of Mechanics Engineering and Civil Architecture,Northwestern Polytechnical Univ.,Xi’an 710072,China

Published:2021-08-15

摘要/Abstract

摘要： 基于数学解析与特征造型技术相结合的方法,建立了基于构造过程的复杂涡轮冷却叶片的参数化设计技术。用五次多项式描述叶身型线,根据壁面厚度函数求解冷却通道外形,定义冷却通道隔板位置及厚度等参数,计算得到叶身及冷却通道各截面造型数据;以特征造型方法完成对涡轮冷却叶片转弯流道、缘板、榫头及叶片相关特征的参数化设计;利用CAD系统的二次开发接口,实现了多腔回流式涡轮冷却叶片的自动建模。

关键词: 航空发动机;参数化设计+;涡轮叶片;特征造型+

Abstract: Based on analytic and feature modeling methods,a parametric design method for three-dimensional internally cooling turbine blade model with ribs and bleed was developed.Blade profiles were defined by five-order polynomial expression.The cooling passage profiles were defined by the thickness of wall according to the blade profiles.A FORTRAN program was written with the intent to provide rapid and robust geometry generation of realistic turbine blades.The ribs,rabbet and margin pale were designed by means of CAD with feature modeling method.As an example,a tri-cavities internal cooling turbine blade was successfully established using this method.

Key words: Aircraft engine;Parametric design+;Turbine blade;Feature modeling+

虞跨海,李立州,岳珠峰. 基于解析及特征造型的涡轮冷却叶片参数化设计[J]. 推进技术, 2007, 28(6): 637-640.